Yuxiang LIM, Thommie NILSSON, Christer FUREBY
DOI Number: XXX-YYY-ZZZ
Conference number: HiSST2024-00174
A series of Large Eddy Simulation (LES) based investigations was performed to analyse a non-premixed
hydrogen-air annular rotating detonation combustor, using a detailed 22-step reaction mechanism and
a finite volume based solver previously-designed for high-speed reacting flows. A specific design and
test configuration from the US Air Force Research Laboratory has been used. The mass flow rate was
maintained at 0.144 kg/s, with a unity global equivalence ratio for the reactant inflows, throughout the
simulations. The results obtained from the single stably-rotating wave, showcase the computational
model’s capability to replicate the principal characteristics of rotating detonation waves. Validation of
the numerical results with available experimental data, shows agreement in magnitude and trend.
Statistical analysis revealed increased temperature and pressure, volumetric expansion, and fuel
suppression during and after the wave sweep, resulting in higher outer wall temperatures in the front
axial half of the combustor. The role of reactant mixing in the studied rotating detonation case was also
evaluated. Wide ranges of temperature and pressure were observed within the combustor, highlighting
the highly dynamic nature of the combustion processes. A significant amount of deflagration was also
found to be present in the chamber, with those occurring ahead of the detonation wave having a
potentially more significant impact on the combustor performance.